CN111174650B - Self-triggering missile-borne data recorder - Google Patents
Self-triggering missile-borne data recorder Download PDFInfo
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- CN111174650B CN111174650B CN202010087799.8A CN202010087799A CN111174650B CN 111174650 B CN111174650 B CN 111174650B CN 202010087799 A CN202010087799 A CN 202010087799A CN 111174650 B CN111174650 B CN 111174650B
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- 230000004913 activation Effects 0.000 claims abstract description 55
- 230000007246 mechanism Effects 0.000 claims abstract description 31
- 238000012360 testing method Methods 0.000 claims abstract description 27
- 238000012545 processing Methods 0.000 claims description 28
- 238000007726 management method Methods 0.000 claims description 27
- 229910000831 Steel Inorganic materials 0.000 claims description 19
- 239000010959 steel Substances 0.000 claims description 19
- 238000013500 data storage Methods 0.000 claims description 15
- 238000005096 rolling process Methods 0.000 claims description 10
- 238000013461 design Methods 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 abstract description 4
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000010304 firing Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 229910052987 metal hydride Inorganic materials 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Recording Measured Values (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a self-triggering missile-borne data recorder which comprises a power supply module, a test recording module and an inertia triggering activation module, wherein the power supply module is connected with the test recording module; the overload signals at specific positions are tested by adopting four low-cost triaxial acceleration sensors, and triaxial overload or overload and rotating speed data at any other positions of the mass center position of the projectile body can be obtained after interpolation conversion; the long pulse width overload of rocket projectile firing is sensed by adopting a double-stroke inertia trigger activation mechanism, and meanwhile, the activation by the small pulse width impact overload trigger in the environment is avoided; the ultra-low power consumption power management module is adopted to uninterruptedly detect two sets of micro switches on the double-stroke inertia trigger activation mechanism, and after the two sets of micro switches on the double-stroke inertia trigger mechanism are detected to act simultaneously, the activation condition is met, and the test recording module starts to be electrified.
Description
Technical Field
The invention belongs to the technical field of data recorders, and particularly relates to a self-triggering missile-borne data recorder.
Background
The flight test of the rocket projectile is an essential link in the development process, and the overload and rotating speed parameters of the rocket projectile in the flight process are tested through the flight test, so that the technical indexes and the ballistic performance of the rocket projectile can be evaluated.
The missile-borne flight data recorder is the most common test recording means, has low cost and simple structure compared with ballistic telemetry recording, does not need auxiliary equipment, and is most suitable for being used as the flight data recording of the rocket shell.
Meanwhile, the flying trajectory of the rocket projectile is characterized by relatively smaller flying overload, long continuous overload pulse width, smaller rotating speed and longer trajectory time. Therefore, there is a need to develop a missile-borne data recorder suitable for low overload, long pulse width, small rotation speed, low cost, automatic triggering, long standby and long recording.
Disclosure of Invention
The present invention aims to solve the above problems by providing a self-triggering missile-borne data recorder.
The invention realizes the above purpose through the following technical scheme:
A self-triggering missile-borne data recorder installed in a rocket projectile, the self-triggering missile-borne data recorder comprising:
A power module; the power module comprises a battery pack and a power management board; the battery pack is respectively and electrically connected with the power management board and the test recording module; the power management board is used for controlling the battery pack to supply power to the test recording module after detecting an activation signal from the double-stroke inertia trigger activation mechanism;
A test recording module;
An inertial trigger activation module; the inertia trigger activation module comprises a double-stroke inertia trigger activation mechanism, and a signal output end of the double-stroke inertia trigger activation mechanism is connected with a signal input end of the power management board; the double-stroke inertia trigger activation mechanism is used for sending an activation signal to the power management board after receiving the overload of rocket projectile emission.
Specifically, the test recording module comprises a data storage board, a signal processing board and a sensor board; the battery pack is respectively and electrically connected with the data storage plate, the signal processing plate and the sensor plate, the sensor plate is used for acquiring rocket projectile flight data, the signal output end of the sensor plate is connected with the signal input end of the signal processing plate, and the signal output end of the signal processing plate is connected with the signal input end of the data storage plate.
Specifically, the self-triggering missile-borne data recorder further includes:
a charging interface; the charging interface is electrically connected with the battery pack;
a data interface; one end of the data interface is in communication connection with the data storage board, and the other end of the data interface is in communication connection with the computer;
An upper cover;
a housing I; the upper cover is arranged on the shell I and forms a closed structure; the charging interface and the data interface are both arranged on the upper cover;
A sensor I;
a sensor II;
A sensor PCB I; the sensor I and the sensor II are arranged on the sensor PCB I; the sensor I and the sensor II are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder;
the data storage board and the signal processing board are combined to form a signal processing board and a storage board; the signal processing and storing board is respectively and electrically connected with the sensor PCB I and the power management board;
a sensor III;
a sensor IV;
Sensor PCB II; the sensor III and the sensor IV are arranged on the sensor PCB II; the sensor III and the sensor IV are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder; the sensor I, the sensor II, the sensor PCB I, the sensor III, the sensor IV, the sensor PCB II, the signal processing and storing board, the battery pack and the double-stroke inertial trigger activation mechanism are all arranged in a closed space formed by the upper cover and the shell I.
Preferably, the sensor PCB I and the sensor PCB II are both arranged perpendicular to the vertical axis of the self-triggering missile-borne data recorder; the self-triggering missile-borne data recorder is coaxially arranged with the rocket projectile.
Preferably, the sensor I and the sensor II are mounted on the inner side of the sensor PCB I; the sensor III and the sensor IV are mounted on the inner side of the sensor PCB II.
Specifically, the dual stroke inertia trigger activation mechanism includes:
a housing II; two mutually parallel sliding channels are formed in the shell II; the sliding channel is arranged in a direction parallel to the vertical axis of the self-triggering missile-borne data recorder;
a front mass; an inward inclined plane is formed on one side of the upper end of the front mass block;
A rear mass; the front mass block and the rear mass block are respectively slidably arranged in the two sliding channels; a circular arc-shaped groove for clamping the steel ball is formed on one side of the lower end of the rear mass block;
A steel ball; the steel ball is arranged in the rolling channel, one part of the steel ball is contacted with one side of the front mass block under the overload action smaller than the design threshold value, and the other part of the steel ball is arranged in the groove of the rear mass block and clamps the rear mass block;
A spring; the two sliding channels are communicated through a rolling channel; the lower end of the front mass block and the lower end of the rear mass block are contacted with the bottom of the sliding channel through a spring; a microswitch I is arranged in one sliding channel, a microswitch II is arranged in the other sliding channel, under the continuous overload effect larger than a design threshold value, the front mass block moves downwards, the front mass block pushes the closed microswitch I, meanwhile, the inclined plane of the front mass block moves downwards to the rolling channel, the steel ball moves leftwards, the rear mass block releases constraint, the rear mass block moves downwards under the overload effect, the microswitch II is closed, and the two microswitches are all closed to trigger an activation instruction and send the activation instruction to a power management board.
Preferably, the battery pack is a rechargeable battery.
The invention has the beneficial effects that:
and testing overload signals at specific positions by adopting four low-cost triaxial acceleration sensors, and obtaining triaxial overload or overload and rotating speed data at any other positions of the mass center of the projectile after interpolation conversion.
The long pulse width overload of rocket projectile firing is sensed by adopting the double-stroke inertia trigger activation mechanism, and meanwhile, the activation by the small pulse width impact overload trigger in the environment is avoided.
The ultra-low power consumption power management module is adopted to uninterruptedly detect two sets of micro switches on the double-stroke inertia trigger activation mechanism, and after the two sets of micro switches on the double-stroke inertia trigger mechanism are detected to act simultaneously, the activation condition is met, and the test recording module starts to be electrified.
Drawings
FIG. 1 is a diagram of an installation of a missile-borne data recorder in a full bullet;
FIG. 2 is a diagram of the configuration of an on-board data logger system;
FIG. 3 is a cross-sectional view of the configuration of the missile-borne data recorder;
FIG. 4 is a cross-sectional view of an inertial trigger activation mechanism of the missile-borne data recorder (in an inactive state);
FIG. 5 is a schematic diagram (transitional state) of the inertial trigger activation mechanism of the missile-borne data recorder;
FIG. 6 is a schematic diagram of the inertial trigger activation mechanism of the missile-borne data recorder (trigger state);
FIG. 7 is a schematic diagram of an on-board data logger system;
In the figure: the device comprises a 1-charging interface, a 2-sensor I, a 3-data interface, a 4-upper cover, a 5-sensor II, a 6-sensor PCB I, a 7-signal processing and storing board, an 8-two-stroke inertial trigger activation mechanism, a 9-battery pack, a 10-sensor III, a 11-housing I, a 12-sensor PCB II, a 13-sensor IV, a 14-power management board, a 15-housing II, a 16-front mass block, a 17-steel ball, a 18-rear mass block, a 19-spring, a 20-micro switch I, a 21-micro switch II and a 22-self-triggering missile-borne data recorder.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
As shown in fig. 2, a self-triggering missile-borne data recorder installed in a rocket projectile, the self-triggering missile-borne data recorder 22 includes:
A power module; the power module comprises a battery pack 9 and a power management board 14; the battery pack 9 is respectively and electrically connected with the power management board 14 and the test recording module; the power management board 14 is used for controlling the battery pack 9 to supply power to the test recording module after detecting an activation signal from the two-stroke inertia trigger activation mechanism 8;
A test recording module;
An inertial trigger activation module; the inertia trigger activation module comprises a double-stroke inertia trigger activation mechanism 8, and a signal output end of the double-stroke inertia trigger activation mechanism 8 is connected with a signal input end of a power management board 14; the two-stroke inertia trigger activation mechanism 8 is configured to send an activation signal to the power management board 14 after receiving a rocket projectile launch overload.
In this embodiment, the power supply module is controlled by using the power management module with ultra-low power consumption, and power is not supplied to the test recording module until the trigger activation signal is not received.
As shown in fig. 2, the test recording module comprises a data storage board, a signal processing board and a sensor board; the battery pack 9 is respectively and electrically connected with the data storage plate, the signal processing plate and the sensor plate, the sensor plate is used for acquiring rocket projectile flight data, the signal output end of the sensor plate is connected with the signal input end of the signal processing plate, and the signal output end of the signal processing plate is connected with the signal input end of the data storage plate.
As shown in fig. 3, the self-triggering missile-borne data recorder 22 further includes:
A charging interface 1; the charging interface 1 is electrically connected with the battery pack 9;
a data interface 3; one end of the data interface 3 is in communication connection with the data storage board, and the other end of the data interface 3 is in communication connection with the computer;
An upper cover 4;
a housing I11; the upper cover 4 is arranged on the shell I11 in a covering way and forms a closed structure; the charging interface 1 and the data interface 3 are both arranged on the upper cover 4;
A sensor I2;
A sensor II 5;
sensor PCB I6; the sensor I2 and the sensor II 5 are arranged on the sensor PCB I6; the sensor I2 and the sensor II 5 are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder 22;
The data memory board and the signal processing board are combined to form a signal processing and memory board 7; the signal processing and storing board 7 is respectively and electrically connected with the sensor PCB I6 and the power management board 14;
Sensor III 10;
A sensor IV 13;
Sensor PCB II 12; sensor III 10 and sensor IV 13 are mounted on sensor PCB II 12; the sensor III 10 and the sensor IV 13 are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder 22; the sensor I2, the sensor II 5, the sensor PCB I6, the sensor III 10, the sensor IV 13, the sensor PCB II 12, the signal processing and storing board 7, the battery pack 9 and the double-stroke inertia trigger activation mechanism 8 are all arranged in a closed space formed by the upper cover 4 and the shell I11.
As shown in fig. 1 and 3, the sensor PCB i 6 and the sensor PCB ii 12 are both arranged perpendicular to the vertical axis of the self-triggering missile-borne data recorder 22; the self-triggering missile-borne data logger 22 is mounted coaxially with the rocket projectile, and the axial mounting location is not limited.
As shown in fig. 3, the sensor i 2 and the sensor ii 5 are mounted on the inner side of the sensor PCB i 6; sensor III 10 and sensor IV 13 are mounted on the inside of sensor PCB II 12.
As shown in fig. 4-6, the two-stroke inertia trigger activation mechanism 8 includes:
a housing II 15; two mutually parallel sliding channels are formed in the shell II 15; the sliding channel is arranged in a direction parallel to the vertical axis of the self-triggering missile-borne data recorder 22;
a front mass 16; an inward inclined surface is formed on one side of the upper end of the front mass block 16;
a rear mass 18; the front mass 16 and the rear mass 18 are slidably disposed in the two sliding channels, respectively; a circular arc-shaped groove for clamping the steel ball 17 is formed on one side of the lower end of the rear mass block 18;
A steel ball 17; the steel ball 17 is arranged in the rolling channel, one part of the steel ball 17 is contacted with one side of the front mass block 16 under the overload action smaller than the design threshold value, and the other part of the steel ball 17 is arranged in a groove of the rear mass block 18 and clamps the rear mass block 18;
a spring 19; the two sliding channels are communicated through a rolling channel; the lower end of the front mass block 16 and the lower end of the rear mass block 18 are contacted with the bottom of the sliding channel through a spring 19; a micro switch I20 is arranged in one sliding channel, and a micro switch II 21 is arranged in the other sliding channel;
as shown in fig. 4, under the continuous overload action greater than the design threshold, the front mass block 16 moves downwards, the front mass block 16 pushes the closed micro switch i 20, and simultaneously the inclined plane of the front mass block 16 moves downwards to the rolling channel;
As shown in fig. 5, the steel ball 17 moves left, the rear mass block 18 is released from constraint, the rear mass block 18 moves downwards under the action of overload, and the micro switch ii 21 is closed;
As shown in fig. 6, both microswitches are closed, triggering an activation command and sending to the power management board 14.
In the embodiment, the double-stroke inertial trigger activation mechanism 8 adopts a structure of two sets of spring 19 mass blocks, and only under the overload action of a long pulse width, the mechanism can simultaneously close two sets of micro switches to give trigger activation signals, so that false triggering of overload of a small pulse width under other environments is avoided.
In some embodiments, the battery pack 9 is a rechargeable battery. The battery 9 is preferably a nickel-metal hydride battery.
In some embodiments, the impact resistance design is carried out inside the missile-borne recorder, and the epoxy resin is encapsulated and reinforced, so that the hard recovery overload of 1X 104g can be born.
The data recorder is based on a low-cost triaxial acceleration sensor design, can test triaxial overload (300 g) at different positions (points A and B, which are shown in figure 1) of the data recorder, can interpolate and convert triaxial overload of the rocket projectile centroid position through the distance X between the points A and B and the centroid position H, and can test the rolling speed (0-50 r/s) of the rocket projectile; the missile-borne data recorder is activated by virtue of rocket projectile emission overload, and requires pulse width (> 20 ms) and overload (> 50 g) to be reliably triggered and activated; the missile-borne data recorder can stand by for about 1 month before being activated, namely after being installed in a fully charged state, the missile-borne data recorder can be selected for a launching test within one month; after trigger activation, the missile-borne data recorder starts to record rocket missile flight data, and the sampling frequency is 10KHz, and the recording duration is longer than 30 min.
In the application, the double-stroke inertia trigger activation mechanism 8 senses rocket projectile launching overload and gives an activation signal to a power management module in the power module; the power supply module consists of a battery pack 9 and a power supply management board 14, and when the power supply management board 14 detects an activation signal, power supply to the test recording module is started; the test recording module is a core component and consists of a sensor board, a signal processing board and a data storage board, and is responsible for acquisition, processing, recording, subsequent reading and the like of rocket projectile flight data.
In the application, the charging interface 1 can charge the data recorder; the data interface 3 is a data interface 3 of a data recorder; the distance between the sensor I2 and the sensor II 5 is R; the signal processing and storing board 7 processes and stores the sensor signals;
Fig. 7 is a schematic diagram of an on-board data logger system. The four sensors are used for respectively testing the three-way overload of the corresponding positions, wherein the overload perpendicular to the installation of the PCB is axial overload, and the overload corresponding to the position of the PCB can be obtained after weighted average. Interpolation is carried out according to the distance X from the point A to the point B and the distance H from the mass center to the missile-borne data recorder in the figure 1, so that the three-way overload of the mass center can be obtained; and vector addition is carried out on radial acceleration components of the sensor to obtain centrifugal force at a corresponding position, then the rotating speeds of the point A and the point B can be calculated according to the distance R between the installation position and the circle center, and the average rotating speed of the projectile body can be obtained after addition and average.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and their equivalents.
Claims (6)
1. The utility model provides a self-triggering missile-borne data record appearance installs in rocket shell, its characterized in that, self-triggering missile-borne data record appearance includes:
A power module; the power module comprises a battery pack and a power management board; the battery pack is respectively and electrically connected with the power management board and the test recording module; the power management board is used for controlling the battery pack to supply power to the test recording module after detecting an activation signal from the double-stroke inertia trigger activation mechanism;
A test recording module;
An inertial trigger activation module; the inertia trigger activation module comprises a double-stroke inertia trigger activation mechanism, and a signal output end of the double-stroke inertia trigger activation mechanism is connected with a signal input end of the power management board; the double-stroke inertia trigger activation mechanism is used for sending an activation signal to the power management board after receiving the overload of rocket projectile emission; the double-stroke inertia trigger activation mechanism comprises a shell II, a front mass block, a rear mass block, a steel ball and a spring; two mutually parallel sliding channels are formed in the shell II; the sliding channel is arranged in a direction parallel to the vertical axis of the self-triggering missile-borne data recorder; an inward inclined plane is formed on one side of the upper end of the front mass block; the front mass block and the rear mass block are respectively slidably arranged in the two sliding channels; a circular arc-shaped groove for clamping the steel ball is formed on one side of the lower end of the rear mass block; the steel ball is arranged in the rolling channel, one part of the steel ball is contacted with one side of the front mass block under the overload action smaller than the design threshold value, the other part of the steel ball is arranged in the groove of the rear mass block, and the two sliding channels are blocked by the rear mass block and are communicated through the rolling channel; the lower end of the front mass block and the lower end of the rear mass block are contacted with the bottom of the sliding channel through a spring; a microswitch I is arranged in one sliding channel, a microswitch II is arranged in the other sliding channel, under the continuous overload effect larger than a design threshold value, the front mass block moves downwards, the front mass block pushes the closed microswitch I, meanwhile, the inclined plane of the front mass block moves downwards to the rolling channel, the steel ball moves leftwards, the rear mass block releases constraint, the rear mass block moves downwards under the overload effect, the microswitch II is closed, and the two microswitches are all closed to trigger an activation instruction and send the activation instruction to a power management board.
2. A self-triggering missile-borne data recorder in accordance with claim 1 wherein: the test recording module comprises a data storage board, a signal processing board and a sensor board; the battery pack is respectively and electrically connected with the data storage plate, the signal processing plate and the sensor plate, the sensor plate is used for acquiring rocket projectile flight data, the signal output end of the sensor plate is connected with the signal input end of the signal processing plate, and the signal output end of the signal processing plate is connected with the signal input end of the data storage plate.
3. A self-triggering missile-borne data recorder in accordance with claim 2, further comprising:
a charging interface; the charging interface is electrically connected with the battery pack;
a data interface; one end of the data interface is in communication connection with the data storage board, and the other end of the data interface is in communication connection with the computer;
An upper cover;
a housing I; the upper cover is arranged on the shell I and forms a closed structure; the charging interface and the data interface are both arranged on the upper cover;
A sensor I;
a sensor II;
A sensor PCB I; the sensor I and the sensor II are arranged on the sensor PCB I; the sensor I and the sensor II are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder;
the data storage board and the signal processing board are combined to form a signal processing board and a storage board; the signal processing and storing board is respectively and electrically connected with the sensor PCB I and the power management board;
a sensor III;
A sensor IV; the sensor I, the sensor II, the sensor III and the sensor IV are all triaxial sensors;
Sensor PCB II; the sensor III and the sensor IV are arranged on the sensor PCB II; the sensor III and the sensor IV are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder; the sensor I, the sensor II, the sensor PCB I, the sensor III, the sensor IV, the sensor PCB II, the signal processing and storing board, the battery pack and the double-stroke inertial trigger activation mechanism are all arranged in a closed space formed by the upper cover and the shell I.
4. A self-triggering missile-borne data recorder in accordance with claim 3, wherein the sensor PCB i and the sensor PCB ii are each disposed perpendicular to a vertical axis of the self-triggering missile-borne data recorder; the self-triggering missile-borne data recorder is coaxially arranged with the rocket projectile.
5. A self-triggering missile-borne data recorder in accordance with claim 3 wherein sensor i and sensor ii are mounted on the inside of sensor PCB i; the sensor III and the sensor IV are mounted on the inner side of the sensor PCB II.
6. A self-triggering missile-borne data recorder in accordance with claim 3 wherein the battery is a rechargeable battery.
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| CN202010087799.8A CN111174650B (en) | 2020-02-11 | 2020-02-11 | Self-triggering missile-borne data recorder |
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